N - s method for solving the flow around a wing with deflection of flap is presented 给出了带襟翼偏转的三维机翼绕流的一种求解n - s方程的计算方法。
A n - s method for solving the flow around a wing with deflection of flap is presented 给出了带襟翼偏转的三维机翼绕流的一种求解n - s方程的计算方法。
The potential flow theory is then applied to the overlap of the slipstream and the flow over the wing 用位流理论来处理螺旋桨滑流与机翼绕流的迭加。
Based on the above grid division and refinement scheme , a computer program named wsmr is developed 依据上述网格离散和加密方案，研制开发了风对建筑绕流的计算机模拟程序wsmr 。
Numerical results show that the present method is effective one for solving the flow around wing with flap deflection 数值算例表明本方法是求解带襟翼偏转的机翼绕流的有效方法。
The large eddy simulation of three dimension circular cylinder shows that : the calculation result fit perfectly to the experiment 三维圆柱绕流的大涡模拟显示:其计算结果与己有的实验结果吻合较好。
The flow field that results from the interaction of lateral jets injection into supersonic flow over projectile has complicated shocks wave patterns , which include regions of shocks and expand waves , and the lateral jet interaction also effects base flow of projectile 弹丸侧喷流与绕流的相互干扰形成了包含喷口前激波、再附激波以及沿喷流边界发展的膨胀波等复杂的波系结构，并延伸影响到弹底部流动。
The paper researches the transient time precision and the following problem of the results developing with time for 2 - d high order blocking and matched method , at the same time , anlysing the stability of high order methods including boundary conditions . the results show that the domain decomposition and matched method using high order method can follow the time developing solution of taylor problem well , the computation result of the flow over a single or two tandem arranging circular cylinder agree the experiment and others " results well , moreover , the panting results of lift and drag coefficient are better than others 本文利用高精度分块耦合求解方法，对其瞬态时间精度和非定常时间发展解的跟随性问题进行了研究，同时也对包含边界条件的线法高精度格式的稳定性也作了分析，研究结果表明高精度的分块耦合求解方法可以很好地跟随taylor问题的时间发展解，与单圆柱绕流和双圆柱绕流的实验结果比较以及他人结果比较符合很好，对升阻力系数在涡脱落时的脉动问题的结果优于他人结果。
Then the steady and unsteady subsonic , transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated . the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm , with baldwin - lomax turbulent model . on the basis of simulating unsteady viscous flow , coupling the structure dynamics equations , the problems of static aeroelasticity and flutter are investigated for wings and elevator 在模拟非定常粘性绕流的基础上，与颤振运动方程相耦合，分别对机翼和全机流固耦合现象中颤振问题进行了研究，准确求解跨音速颤振临界速度，分析机翼和全机的从亚音速到超音速范围的颤振规律，并研究分析了机翼飞行迎角变化对颤振速度的影响。
